Engine - High-Pressure Turbine (HPT) Stage 1 and HPT Stage 2 Disks - Replacement
- Published
- Effective
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What to do
Operators must remove and replace affected HPT stage 1 and stage 2 disks identified by part and serial numbers before further flight or at the next piece part exposure, depending on the disk and its cycle count. For HPT stage 1 disks exceeding 8,550 cycles since new, replacement may be deferred up to 50 flight cycles after the effective date. The AD becomes effective on June 24, 2025, and compliance must be ensured by that date.
Summary
The Federal Aviation Administration's Airworthiness Directive 2025-10-11 addresses certain General Electric Company Model CF6-80E1A2, CF6-80E1A3, CF6-80E1A4, and CF6-80E1A4/B engines. It mandates the replacement of specific high-pressure turbine (HPT) stage 1 and stage 2 disks identified by part and serial numbers due to manufacturing defects involving iron inclusion. This directive aims to prevent potential uncontained engine failures caused by premature disk fracture.
What changed
This new airworthiness directive introduces mandatory replacement requirements for affected HPT stage 1 and stage 2 disks that were manufactured with powder metal material containing iron inclusions. It specifies compliance timelines including immediate removal before further flight for certain serial numbers and replacement at the next piece part exposure or before reaching specified cycle limits for others. The directive also clarifies that removed parts are not eligible for reinstallation on any engine.
Why it matters
This directive is critical for aviation professionals as it addresses a latent manufacturing defect that could lead to catastrophic engine failures. Operators and maintenance organizations must ensure timely identification and replacement of affected parts to maintain engine integrity and flight safety. Compliance with this AD helps prevent uncontained debris release, protecting aircraft, passengers, and crew from potential harm.
More for General Electric CF6-80E1
All 4- EASA AD US-2023-18-04Forward Outer Seals, High Pressure Turbine Rotor Stage 1 Discs and Rotating Seals - ReplacementOct 13, 2023
- EASA AD US-2020-22-02Engine Fuel and Control - Hydromechanical Unit - Removal / ReplacementOct 30, 2020
- EASA AD US-2020-13-08Engine - High Pressure Compressor Case - InspectionJul 8, 2020
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